A New Strategy of Guidance Command Generation for Re-entry Vehicle

Xie Daocheng; Wang ZhongWei; Zhang WeiHua

doi:10.14429/dsj.63.2360

Xie Daocheng National University of Defense Technology, Changsha
Wang ZhongWei National University of Defense Technology, Changsha
Zhang WeiHua National University of Defense Technology, Changsha

DOI: https://doi.org/10.14429/dsj.63.2360

Keywords: Re-entry homing vehicle, radar seeker, attack angle, sideslip angle, Euler angles, transformation matrix

Abstract

Guidance command for re-entry vehicle can be in lots of formats, but the Euler angles can be provided directly by gyros, so designers used to develop autopilot with commands of Euler angles. After the generation of commands of attack angle and sideslip angle, it’s important to settle how to convert commands of attack angle and sideslip angle to commands of Euler angles. Traditional conversion strategy relies on bank angle, solution to bank angle comprises complicated calculation and can’t be precise. This paper introduces a new conversion strategy of guidance command. This strategy relies on the relative position and velocity measured by seeker, an auxiliary coordinateis established as a transition, the transformation matrix from launch coordinate to body coordinate is solved in a new way, then the commands of Euler angles are obtained. The calculation of bank angle is avoided. The autopilot designed with the converted Euler-angle commands, can track commands of attack angle and sideslip angle steadily.The vehicle reaches the target point precisely. Simulation results show that the new conversion strategy based on seeker information from commands of attack angle and sideslip angle to Euler-angle commands is right.

Defence Science Journal, 2013, 63(1), pp.93-100, DOI:http://dx.doi.org/10.14429/dsj.63.2360

Author Biographies

Xie Daocheng, National University of Defense Technology, Changsha

Mr Daocheng Xie obtained his MS from National University of Defense Technology, Changsha, China, in 2008. He is currently pursuing PhD from NUDT. His research interests are: Guidance and attitude control of aircrafts hardware-in-the-loop simulation for flight control.

Wang ZhongWei, National University of Defense Technology, Changsha

Dr Zhongwei Wang obtained his PhD from National University of Defense Technology in 1995, presently, working as a Professor at College of Aerospace Science and Engineering, National University of Defense Technology. His research areasare: Navigation, guidance and attitude control of aircrafts and spacecrafts.

Zhang WeiHua, National University of Defense Technology, Changsha

Dr Weihua Zhang obtained his PhD from National University of Defense Technology in 1999, presently, working as a Dean and Professor of College of Aerospace Science and Engineering, National University of Defense Technology. His research areas are: Advanced attitude control method, multi-disciplinary optimizationon aircraft design.